CN104662258B - Gas turbine system and operation include the method for the gas turbine system of load - Google Patents
Gas turbine system and operation include the method for the gas turbine system of load Download PDFInfo
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- CN104662258B CN104662258B CN201380041258.XA CN201380041258A CN104662258B CN 104662258 B CN104662258 B CN 104662258B CN 201380041258 A CN201380041258 A CN 201380041258A CN 104662258 B CN104662258 B CN 104662258B
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- 238000000034 method Methods 0.000 title claims description 17
- 239000000567 combustion gas Substances 0.000 claims abstract description 94
- 239000007789 gas Substances 0.000 claims abstract description 55
- 238000001816 cooling Methods 0.000 claims description 20
- 239000012530 fluid Substances 0.000 claims description 18
- 230000008878 coupling Effects 0.000 claims description 13
- 238000010168 coupling process Methods 0.000 claims description 13
- 238000005859 coupling reaction Methods 0.000 claims description 13
- 238000002485 combustion reaction Methods 0.000 claims description 9
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 5
- 239000003345 natural gas Substances 0.000 claims description 4
- 238000012545 processing Methods 0.000 claims description 2
- 239000003507 refrigerant Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims 1
- 239000007788 liquid Substances 0.000 description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 230000004048 modification Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 3
- 238000002224 dissection Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 230000008676 import Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000003570 air Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 239000000498 cooling water Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003949 liquefied natural gas Substances 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000000638 solvent extraction Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/0002—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures characterised by the fluid to be liquefied
- F25J1/0022—Hydrocarbons, e.g. natural gas
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J1/00—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
- F25J1/02—Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen ; Details and kind of the refrigeration system used; Integration with other units or processes; Controlling aspects of the process
- F25J1/0243—Start-up or control of the process; Details of the apparatus used; Details of the refrigerant compression system used
- F25J1/0279—Compression of refrigerant or internal recycle fluid, e.g. kind of compressor, accumulator, suction drum etc.
- F25J1/0281—Compression of refrigerant or internal recycle fluid, e.g. kind of compressor, accumulator, suction drum etc. characterised by the type of prime driver, e.g. hot gas expander
- F25J1/0283—Gas turbine as the prime mechanical driver
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/60—Shafts
- F05D2240/61—Hollow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/33—Arrangement of components symmetrical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J2230/00—Processes or apparatus involving steps for increasing the pressure of gaseous process streams
- F25J2230/20—Integrated compressor and process expander; Gear box arrangement; Multiple compressors on a common shaft
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J2270/00—Refrigeration techniques used
- F25J2270/12—External refrigeration with liquid vaporising loop
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
- F25J2270/00—Refrigeration techniques used
- F25J2270/90—External refrigeration, e.g. conventional closed-loop mechanical refrigeration unit using Freon or NH3, unspecified external refrigeration
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Eletrric Generators (AREA)
Abstract
The present invention discloses a kind of gas turbine system, at least the first load (71) and the second load (72) that the gas turbine system includes combustion gas turbine (23), energized by the combustion gas turbine.The combustion gas turbine (23) includes：Gas generator (27)；Low-pressure turbine (50)；The line shaft (65) energized by low-pressure turbine (50).The line shaft, which has, to be drivingly connected to the first shaft end (65H) of first load and is drivingly connected to the second axle (65C) of second load.First load and second load are arranged at the opposite side of the combustion gas turbine, and the line shaft (65) extends axially through the combustion gas turbine from the first end of the combustion gas turbine to the second end.
Description
Technical field
The disclosed embodiments relate generally to combustion gas turbine.More properly, embodiment be related to including combustion gas turbine and
The system of the load (such as generator or compressor) driven by the combustion gas turbine.
Background technology
Combustion gas turbine is typically used as the machine power generator for driving various operation machines.More precisely
Ground, combustion gas turbine is generally used for driving big turbo-machine, such as Axial Flow Compressor or centrifugal compressor.Typically, combustion gas
Purposes of turbine application is in natural gas liquefaction (LNG), CO2In the field of the other industry of recovery and gas industry.Combustion gas turbine
It additionally may act as the machine power generator for driving generator.
Fig. 1 show according to prior art include combustion gas turbine and the compressor set driven by combustion gas turbine be
System.
Combustion gas turbine is as being generally indicated at 1, and including gas generator 2 and power turbine 3.Gas generator 2
Including by means of axle 6 air compressor 4 and high-pressure turbine 5 mechanically connected to each other.The air sucked by compressor 4 is compressed to
High-voltage value, and it is delivered to the burner schematically shown with 7.Fuel is mixed with the compressed air in burner 7, and
Mixture burning is in the burning gases stream of high temperature and high pressure to produce.
High temperature and high pressure burning gases expand in high-pressure turbine 5 to be used to drive air compressor 4 by axle 6 to produce
Machine power.The burning gases of demi-inflation are further delivered to power turbine 3, and in power turbine 3, they are further
Expand to produce other machine power obtainable on line shaft 9.Discharged burning gases then by soaker 11 come
Discharge.
The machine power produced by high-pressure turbine 5 is entirely used for driving air compressor 4, and is produced by power turbine 3
Machine power can obtain to drive as being generally indicated at 13 load on line shaft 9.In the example shown, load 13 includes
Compressor set.Compressor set is made up of the first compressor 15 and the second compressor 17, such as natural gas liquefaction system it is centrifugal
Compressor.In the schematically showing of Fig. 1, two arranged in series of compressor 15 and 17 and driven at the same speed：It is dynamic
Power is transferred to the first compressor 15 by the load shaft coupling 18 including connector 19, and passes through the second connector 21 from first
Compressor 15 is transferred to the second compressor 17.
This arrangement has some shortcomings.Specifically, load shaft coupling 18 must be for needed for driving compressor 15 and 17
Maximum power be sized and design.If in addition, compressor is so-called vertical subdivision type, i.e., with by along hanging down
The housing that two or more parts of straight partitioning plane connection are formed, opening the housing of the first compressor 15 needs mobile second
Compressor 17 is away from the first compressor 15.
The content of the invention
According to embodiment there is provided a kind of gas turbine system, the gas turbine system include combustion gas turbine with
And at least the first load and the second load energized by combustion gas turbine.Combustion gas turbine includes：Gas generator；Low pressure whirlpool
Wheel；The line shaft energized by low-pressure turbine.Line shaft has the first shaft end for being drivingly connected to the first load and drivingly connected
It is connected to the second shaft end of the second load.Foregoing first load and the second load are arranged at the opposite side of combustion gas turbine, and
Line shaft extends axially through combustion gas turbine from the first end of combustion gas turbine to the second end.
In certain embodiments, combustion gas turbine is that boat changes combustion gas turbine.
First shaft end and the second shaft end are generally disposed at the so-called hot junction of combustion gas turbine and cold end.Combustion gas turbine
Hot junction is the end at soaker, i.e., left in burning gases on the outlet side of low-pressure turbine.The cold end of combustion gas turbine is
Inlet plenum is arranged the end at place.
Term low-pressure turbine indicates a part for turbomachinery, at this part, the burning produced by gas generator
Gas expansion is available for the power that load drives purpose to produce on line shaft.Term " low pressure " is generally used for distinguishing whirlpool
This part of wheel mechanical and the first high-pressure turbine for being just arranged in combustion chamber downstream, at the first high-pressure turbine, high pressure-temperature
Burning gases experience first expands, and for driving gas generator axle to rotate, this drives gas turbine engine compressor in turn.
According to some embodiments, combustion gas turbine includes the following for combining and arranging in proper order：Low pressure compressor；It is high
Compressor is pressed, high pressure compressor is arranged in low pressure compressor downstream and receives the air compressed by the low pressure compressor；Combustion
Burner, burner arrangement is used to receive compressed air and fuel gas or liquid fuel from the second high pressure compressor；It is high
Turbine is pressed, high-pressure turbine receives the burning gases from burner, and arranges for from the burning partly expanded wherein
Gas produces machine power, and high-pressure turbine is in fluid communication with low-pressure turbine.Burning gases from high-pressure turbine are in low-pressure turbine
Middle expansion.Combustion gas turbine further comprises the second axle for being drivingly connected high-pressure turbine and high pressure compressor.Line shaft and
Two axles are coaxially arranged, and line shaft is drivingly connected low-pressure turbine and low pressure compressor.
In certain embodiments, exhaust arrangement may be provided between low pressure compressor and high pressure compressor.
In certain embodiments, the first load and the second load include the first compressor and the second compressor respectively.It is foregoing
At least one in first compressor and the second compressor may include vertical subdivision housing, you can be cartridge type compressor.One
In a little embodiments, the first compressor and the second compressor both include corresponding vertical subdivision housing, i.e., each compressor is cylinder
Formula compressor.
In other embodiments, one in the first load or the second load includes the compression with vertical subdivision housing
Machine, is cartridge type compressor, and another in first load and second load includes different machines, for example, send out
Motor.
By the way that two load to be arranged to be drivingly coupled to the opposite end through axle of combustion gas turbine, level is substituted
Dissection type compressor, can be used vertical dissection type compressor.This causes higher system effectiveness.
Compressor can be arranged and be configured at least one of processing natural gas liquefaction (LNG) system refrigerant gas.
LNG systems generally include one or more compressor sets, each compressor set driven by one or more combustion gas turbines and
Including one or more compressors.For storing and/or transporting purpose, compressor, which is used to compress, to be used to make natural air cooling and liquid
One or more different refrigerating fluids of change.Therefore, some embodiments of this disclosure include：Combustion gas turbine；At least
Two compressors, at least two compressors are driven by combustion gas turbine and are arranged in the opposite end of turbine, i.e., in turbine
At the hot junction of machine and cold end；At least one refrigerating circuit, refrigerating fluid flows wherein, and the refrigerating fluid is in aforementioned compressor
At least one compresses and flowed at least one heat exchanger needs liquefied natural gas for cooling.
In other embodiments, air cooling system sets, configured and arranges enters gas generator for cooling down
Air stream.Cooling system includes refrigerating circuit, and refrigerating circuit has the compressor for handling the refrigerating fluid circulated in refrigerating circuit.
The compressor of refrigerating circuit is mechanically connected to the first shaft end and the second shaft end of combustion gas turbine, so as to be formed by combustion gas turbine
One in foregoing first load and the second load of energy supply.In certain embodiments, cooling system further comprises heat exchange
Device, wherein the refrigerating fluid circulated in refrigerating circuit and the second fluid heat-shift flowed in the second loop.Described second
Loop includes fluid/air exchanger, wherein the combustion air for being delivered to combustion gas turbine passes through with flowing in the second loop
Second fluid heat-shift and be cooled.From the heat transmission of air stream extraction to the refrigeration in the evaporator of refrigerating circuit
Liquid.
In a preferred embodiment, the driven compressor of cooling circuit it is connected at the cold end of combustion gas turbine
First shaft end.
In different embodiments, at least one in the first load and the second load includes generator.In some embodiments
In, generator arrangements and it is configured to power for the servicing unit of combustion gas turbine.Generator is connected drivably to power
First shaft end of the axle at the cold end of the combustion gas turbine.
According on the other hand, the present invention relates to the method for operating gas turbine system.
According to some embodiments there is provided a kind of method for operating gas turbine system, it the described method comprises the following steps：
There is provided gas generator, low-pressure turbine and line shaft, line shaft has respectively can be the of the combustion gas turbine
The first shaft end and the second shaft end accessed at one end and the second end；
First load is drivingly connected to the first shaft end, and the second load is drivingly connected to the second shaft end；
Machine power is produced by means of low-pressure turbine；
The Part I of the power produced by low-pressure turbine is used to by the first load shaft coupling to drive the first load, and
And be used to the Part II of the power produced by low-pressure turbine by the second load shaft coupling drive the second load.
Propose in the dependent claims and the other implementation of the method according to the invention is being described below with reference to accompanying drawing
Example.
The feature that set forth various embodiments of the present invention is mentioned briefly above, it is described further below to be better understood
And contribution of the present invention to art can be best understood from.Certainly, exist will thereafter description and will be in appended right
Other features of the invention stated in claim.Thus, should before some embodiments of the present invention are explained in detail
Understand, various embodiments of the present invention are not limited to apply them to construction stating in following explanation or being shown in the drawings
The arrangement of details and part.The present invention can have other embodiment and can be practiced and carried out in a variety of ways.In addition, should
Understand, the phrase and term that this specification is used are used to illustrate, and are not construed as limitation.
Therefore, those skilled in the art will appreciate that, can easily be set based on the basic concept of this specification
Count other structures, method and/or the system for realizing some purposes of the invention.It is important, therefore, that claims by regarding
It is to include such equivalent constructions, as long as these equivalent constructions are without departing substantially from the spirit and scope of the present invention.
Brief description of the drawings
Described further below disclosure of the invention embodiment can be best understood from due to being read in conjunction with the figure and many attached
Band advantage, therefore, it is possible to be more fully understood from these embodiments and advantage, in the accompanying drawings：
Fig. 1 shows schematically showing according to the system of prior art；
Fig. 2 is shown along the cross section of combustion gas turbine axial plane useful in a system in accordance with the invention；
Fig. 3, Fig. 4 and Fig. 5 show schematically showing for the system according to the present invention.
Embodiment
Exemplary embodiment is described in detail hereinafter with reference to accompanying drawing.Same reference numbers in different accompanying drawings refer to it is identical or
Similar element.In addition, the accompanying drawing is not drawn necessarily to scale.In addition, described in detail below be not intended to limit the present invention.Phase
Instead, it is intended that the scope of the present invention be defined by the claims appended hereto.
The reference of " one embodiment " or " embodiment " or " some embodiments " is represented to combine in entire disclosure
Specific features, structure or the characteristic of the embodiment description are included at least one embodiment of disclosed theme.
Therefore, the phrase " in one embodiment " or " in one embodiment " that different places occur in entire disclosure might not
Refer to identical embodiment.In addition, specific features, structure or characteristic can be combined in one or more realities in any way as suitable
Apply in example.
Fig. 2 shows that the boat for using in a system in accordance with the invention changes the vertical section of combustion gas turbine 23.Combustion gas whirlpool
Turbine 23 includes gas generator section 27, and gas generator section 27 is included with one group of fixation inlet vane being located at suction side
33 low pressure Axial Flow Compressor 31.Multiple low pressure compression stages 35 are arranged in the fixed downstream of inlet vane 33.Each low pressure compression
Level 35 includes one group of rotating vane and one group of fixation blade.Rotating vane is supported by low pressure compressor rotor 37, and fixed leaf
Piece is supported by the shell of low pressure Axial Flow Compressor 31.
Low pressure Axial Flow Compressor 31 and the high pressure Axial Flow Compressor 39 for being arranged in the downstream of low pressure Axial Flow Compressor 31
It is in fluid communication.High pressure Axial Flow Compressor 39 includes multiple high pressure compresseds level 43.Each high pressure compressed level 43 includes one group of rotation
Blade and one group of fixation blade.Rotating vane is supported by high pressure compressor rotor 45.Fixed blade is by high pressure Axial Flow Compressor
39 housing support.
The outlet of high pressure Axial Flow Compressor 39 is in fluid communication with burner 47.Pressure from high pressure Axial Flow Compressor 39
Stream of compressed air is moved in the burner 47 and fuel gas or liquid fuel are mixed with compressed air, and air/fuel
Mixture is ignited to generate the hot combustion gas of compression.
In the downstream of burner 47, the first high-pressure turbine 49 is arranged to be in fluid communication with burner 47.High-pressure turbine 49 includes
One group of fixation inlet vane 48, is each to include one or more expansion stages of one group of fixation blade and one group of rotating vane afterwards
51.Rotating vane is supported by High Pressure Turbine Rotor 53.High Pressure Turbine Rotor 53 and high pressure compressor rotor 45 are by gas generator
Axle 55 support and torsion be limited to gas generator axle 55.
The burning gases expansion for flowing through high-pressure turbine 49 from burner 47 produces machine power, and the machine power is driven
Move gas generator axle 55 and for being energized for high pressure Axial Flow Compressor 39.
The outlet of high-pressure turbine 49 is connected with the inlet fluid of low-pressure turbine 50.Flow through the combustion gas of high-pressure turbine 49
Body only partially expands, and their expansion continues in low-pressure turbine 50.The import of low-pressure turbine 50 is included by turbine
One group of fixation blade 59 of the housing support of tool, is multiple inflated with low pressure levels 61 afterwards.Each inflated with low pressure level 61 includes one group
Rotating vane and one group of fixation blade.Rotating vane is supported by Low Pressure Turbine Rotor 63, and fixed blade is by combustion gas turbine
23 housing support.Low Pressure Turbine Rotor 63 is rotatably limited to line shaft 65 and supported by line shaft 65.Line shaft 65 prolongs
Extend through combustion gas turbine and extended coaxially into gas generator axle 55.Low pressure compressor rotor 37 is by same line shaft 65
Support and be limited to same line shaft 65.
The burning gases expanded in low-pressure turbine 50 produce the obtainable machine power on line shaft 65, and part
Ground is used to drive low pressure Axial Flow Compressor 31.Power more than power needed for driving low pressure Axial Flow Compressor 31 can be used for driving
Dynamic loading.
Such as from Fig. 2 it can be appreciated that line shaft 65 extends to opposite second end 65H from first end 65C.The first end of line shaft 65
65C is arranged at the so-called cold end of combustion gas turbine 23 or cold side 23C, i.e., at the inlet of cold air side of combustion gas turbine 23.
Second end 65H is arranged at the so-called hot junction of combustion gas turbine 23 or hot side 23H, i.e., at following side：In high-pressure turbine 49
After being expanded in low-pressure turbine 50, discharge hot combustion gas and be discharged from the side at 67.
The combustion gas turbine 23 of species shown in Fig. 2 can be used in the system that Fig. 3 is schematically shown.
In addition to combustion gas turbine 23, system includes the first load 71 and the second load 72.In Fig. 3 exemplary embodiment
In, the first load 71 and the second load 72 both such as centrifugal compressor of LNG pipelines.One, another or two
Compressor 71 and 72 can be vertical subdivision type, have features designed to along the housing for extending vertically plane opening.Due to two
Compressor 71 and 72 is connected on the opposite side of combustion gas turbine 23, and each of which can be for repairing or maintenance purpose easily
Open, without dismounting, remove and another compressor of dislocation.
First compressor 71 is connected to hot junction or the hot side 65H of combustion gas turbine 23, shaft coupling by load shaft coupling 67H
67H includes such as connector, potentially includes clutch or the like.
Second compressor 72 is connected to the cold end or cold side 65C of combustion gas turbine 23 by means of the second load shaft coupling 67C,
Second load shaft coupling 67C includes such as connector, clutch or both.
In the exemplary embodiment shown in Fig. 3, two compressors 71 and 72 are with low-pressure turbine 50 in identical rotary speed
Driven down and in the same direction.In other embodiment (not shown), gear-box may be provided at load shaft coupling 67H with
Between associated compressors 71 and/or between load shaft coupling 65C and compressor 72.Gear-box can be used for making direction of rotation reverse
And/or the ratio between modification turbine rotational speed and the rotary speed of associated compressors 71 and/or 72.
In other embodiment (not shown), if more than two compressor must be driven by same combustion gas turbine 23,
One or more other compressors may be arranged at one or both ends 65H, 65C of combustion gas turbine 23.
Fig. 4 shows the second embodiment of the system according to the present invention.Identical reference numeral is indicated identical with Fig. 3 or waited
The part of effect.More properly, Fig. 4 embodiment includes combustion gas turbine 23, and combustion gas turbine 23 includes the He of gas generator 27
Low-pressure turbine 50.
Fig. 4 combustion gas turbine 23 can be the identical type shown in Fig. 2.The various parts to combustion gas turbine 23 are not entered
Row is described again.
In the fig. 4 embodiment, the first load 71 and the second load 73 are drivingly connected to combustion gas turbine 23 respectively
Hot side or hot junction 65H and cold side or cold end 65C.In the embodiment shown in fig. 4, the first load 71 is compressor again, for example
Centrifugal compressor, and the second load 73 is generator.Generator 73 may be connected to power distribution network 74.Power network 74 can be local
Net, for for be connected to the equipment that combustion gas turbine 23 and/or combustion gas turbine 23 are arranged therein electric utility energize.
In Fig. 4 exemplary embodiment, gear-box 76 is arranged between combustion gas turbine 23 and generator 73, to increase rotation speed
Degree.Compressor 71 can be schematically shown in vertical dissection type compressor, such as accompanying drawing again.
In Fig. 4 exemplary embodiment, compressor 71 is arranged at the hot junction of combustion gas turbine 23, and the cloth of generator 73
Put at the cold end of combustion gas turbine 23.In other embodiments, the position of two load 71,73 can be overturned：Compressor is arranged
At the hot junction of combustion gas turbine and generator arrangements are at the hot junction of combustion gas turbine.
Fig. 5 schematically shows other system, and the system includes combustion gas turbine 23 as shown, for example, in fig. 2, the
One load 71 and the second load 72.In the example shown in Fig. 5, the first load 71 is compressor, such as centrifugal compressor again
Machine, by the line shaft 65 of combustion gas turbine 23 by being arranged in the hot junction of combustion gas turbine 23 or hot side 65H load shaft coupling
Device 67H drives.
In this embodiment, the second load 72 includes the compressor of cooling system 81, cooling system 81 be designed and
Arrange the combustion air for entering combustion gas turbine 23 for cooling down.
In the embodiment shown in fig. 5, cooling system 81 includes refrigerating circuit 83, and refrigerating circuit 83 includes above-mentioned
The evaporator 87 of a part for compressor 72, condenser 85, expander or choke valve 86 and formation heat exchanger 88.Refrigerating fluid
Circulated in refrigerating circuit 83, compressed by compressor 72 and condensed in condenser 85, by means of for example with air or water
Heat exchange to remove heat from the refrigerating fluid in condenser 85.Cold and condensation refrigerating fluid is then swollen in expander 86
It is swollen, and the liquid removal heat for flowing through evaporator 87 to be circulated from second servo loop 89.Followed in second servo loop 89
The liquid of ring can be for example cooling water.
Second servo loop 89 includes pump 91, and pump 91 makes coolant such as water circulation pass through heat exchanger 93, the quilt of heat exchanger 93
It is arranged in the coolant heat-shift with being circulated in refrigerating circuit 83 in heat exchanger 88.The water cooled down in heat exchanger 88
The second heat exchanger 95 being arranged at the import of air intake duct 97 is subsequently flowed through, combustion air is passed through by compressor 31 and 39
Air intake duct 97 is sucked.By this way, combustion air contact water heat exchanger 95, water heat exchanger 95, which is cooled air to, to be less than
The temperature of environment temperature, so as to improve the gross efficiency of combustion gas turbine 23.In advantageous embodiment, cooling system 81 can be controlled
To cause combustion air to be maintained at generally constant sky when entering the inlet plenum at the cold end of combustion gas turbine 23
At a temperature of gas, the air themperature is set to maximize the gross efficiency of combustion gas turbine 23.
Therefore, Fig. 5 shows integrated cooling system, and the compressor of wherein cooling circuit is directly driven by combustion gas turbine.Can
Save the separation motor for driving cooling compressor, so that the system is simpler, less heavy and with reduction
Floor space.
In unshowned modification embodiment, the load 71 of the system shown in Fig. 5 can be generator rather than compressor.
Although the open embodiment of theme has been illustrated in the accompanying drawings described in this specification, and above in association with some
Exemplary embodiment is specific and completely describes in detail, but those of ordinary skill in the art are well understood, substantially
Without departing substantially from the advantage of institute's subject matter recited in novel teaching, principle and concept and the appended claims illustrated in this specification
In the case of, many modifications can be made, changes and omits.Therefore, proper range of the invention should be only by appended claims
The broadest explanation of book is determined, to cover all such modifications, to change and omission.In addition, according to each alternate embodiment, appointing
What technique or the order of method and step can be changed or resequence.
Claims (18)
1. a kind of gas turbine system, the gas turbine system includes combustion gas turbine, supplied by the combustion gas turbine
At least the first load and the second load of energy；Wherein described combustion gas turbine includes：
Gas generator；
Low-pressure turbine；
The line shaft energized by the low-pressure turbine, the line shaft has the first axle for being drivingly connected to first load
The second shaft end of second load is held and is drivingly connected to, first load and second load are arranged in the combustion
At the opposite side of gas turbine, and the line shaft is extended axially through from the first end of the combustion gas turbine to the second end
The combustion gas turbine, wherein at least one in first load and second load includes the first compressor；And
Wherein described first compressor includes vertical subdivision housing.
2. system according to claim 1, wherein the gas generator includes at least one air compressor, burner
And high-pressure turbine, the burner arrangement is for receiving compressed air and combustion from least one air compressor
Material, the burning gases produced by the burner expand in the high-pressure turbine；Wherein described line shaft and described at least one
Individual air compressor and the high-pressure turbine are extended coaxially into.
3. the system according to claim 1 or claim 2, wherein the combustion gas turbine is following including what is arranged in proper order
Every combination：
Low pressure compressor；
High pressure compressor, the high pressure compressor is arranged in the low pressure compressor downstream and received by the low pressure pressure in proper order
The air of contracting machine compression；
Burner, the burner arrangement is used to receive compressed air and fuel from the high pressure compressor；
High-pressure turbine, the high-pressure turbine receives the burning gases from the burner, and arranges for from the middle
The burning gases of ground expansion are divided to produce machine power, the high-pressure turbine and low-pressure turbine fluid communication, from institute
The burning gases for stating high-pressure turbine expand in the low-pressure turbine；
Second axle, second axle is drivingly connected to the high-pressure turbine and the high pressure compressor；
Wherein described line shaft and second axle are coaxially arranged, and the line shaft is drivingly connected the low-pressure turbine
With the low pressure compressor.
4. system according to claim 3, the system includes being located at the low pressure compressor and the high pressure compressor
Between exhaust arrangement.
5. system according to claim 1, wherein another in first load and second load includes the
Two compressors.
6. system according to claim 5, wherein second compressor includes corresponding vertical subdivision housing.
7. system according to claim 1, wherein second load includes generator.
8. system according to claim 5, wherein at least one in first compressor and second compressor
Arrange and be configured at least one of processing natural gas liquefaction system refrigerant gas.
9. system according to claim 1, the system, which includes arrangement, is used for the air to entering the gas generator
Flow the air cooling system cooled down；Wherein described air cooling system includes refrigerating circuit, and the refrigerating circuit has place
Manage the compressor of the refrigerating fluid circulated in the refrigerating circuit；And the compressor machinery of wherein described refrigerating circuit is even
One in first shaft end and second shaft end is connected to, so as to form described first energized by the combustion gas turbine
One in load and second load.
10. system according to claim 1, wherein the first axle end is arranged at the cold end of the combustion gas turbine,
And second shaft end is arranged at the hot junction of the combustion gas turbine.
11. system according to claim 9, wherein the driven compressor of the refrigerating circuit be connected to described
First shaft end at the cold end of combustion gas turbine.
12. system according to claim 7, wherein the generator arrangements and being configured to as the combustion gas turbine
Servicing unit power.
13. system according to claim 7, wherein the generator drive be connected to the line shaft in the combustion gas
First shaft end at the cold end of turbine.
14. system according to claim 1, wherein the combustion gas turbine, which is boat, changes combustion gas turbine.
15. a kind of method for operating the gas turbine system for including load, the described method comprises the following steps：
There is provided gas generator, low-pressure turbine and line shaft, the line shaft has respectively can be the of the combustion gas turbine
The first shaft end and the second shaft end accessed at one end and the second end；
First load is drivingly connected to first shaft end, and the second load is drivingly connected to second axle
End；
Machine power is produced by means of the low-pressure turbine；
The Part I of the machine power is used to by the first load shaft coupling to drive first load, and passes through the
The Part II of the machine power is used to drive second load by two load shaft couplings, wherein first load and institute
At least one stated in the second load includes at least one associated compressors with vertical subdivision housing.
16. method according to claim 15, methods described includes：The machinery produced by the low-pressure turbine is dynamic
At least one in the Part I and the Part II of power changes into electric power.
17. the method according to claim 15 or claim 16, the described method comprises the following steps：
Sequentially in the first low pressure compressor under first pressure value and in the second high pressure compressor higher than described
The second pressure value compressed air of one pressure value；
By the air delivery compressed under the second pressure value to burner,
Burning gases are produced in the burner；
The burning gases are made to be expanded in high-pressure turbine；
By means of the high-pressure turbine by driving second high pressure compressor with the second coaxial axle of the line shaft；
Make to expand in the low-pressure turbine from the burning gases that the high-pressure turbine is discharged；
First low pressure compressor is driven by the line shaft by means of the low-pressure turbine；
Obtainable machine power it will partly be delivered to first load on the line shaft and partly be delivered to
Second load.
18. method according to claim 15, methods described includes：The compression of cooling system is driven by the line shaft
Machine, wherein the cooling system includes the compressor for being drivingly connected to one end of the line shaft；And wherein described cooling
System cools down the inlet air flow for being delivered to the combustion gas turbine.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT000161A ITFI20120161A1 (en) | 2012-08-03 | 2012-08-03 | "DUAL-END DRIVE GAS TURBINE" |
| ITFI2012A000161 | 2012-08-03 | ||
| PCT/EP2013/066168 WO2014020104A1 (en) | 2012-08-03 | 2013-08-01 | Dual-end drive gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104662258A CN104662258A (en) | 2015-05-27 |
| CN104662258B true CN104662258B (en) | 2017-10-24 |
Family
ID=46939769
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380041258.XA Active CN104662258B (en) | 2012-08-03 | 2013-08-01 | Gas turbine system and operation include the method for the gas turbine system of load |
Country Status (11)
| Country | Link |
|---|---|
| US (1) | US20150176485A1 (en) |
| EP (1) | EP2880266B1 (en) |
| JP (1) | JP2015524532A (en) |
| KR (1) | KR20150038412A (en) |
| CN (1) | CN104662258B (en) |
| AU (1) | AU2013298557B2 (en) |
| BR (1) | BR112015001404B1 (en) |
| CA (1) | CA2880462C (en) |
| IT (1) | ITFI20120161A1 (en) |
| RU (1) | RU2642714C2 (en) |
| WO (1) | WO2014020104A1 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170107845A1 (en) * | 2015-10-15 | 2017-04-20 | General Electric Company | Systems and methods to facilitate enhancing turbine output using an auxiliary generator |
| ITUB20155049A1 (en) | 2015-10-20 | 2017-04-20 | Nuovo Pignone Tecnologie Srl | INTEGRATED TRAIN OF POWER GENERATION AND COMPRESSION, AND METHOD |
| US10557414B1 (en) * | 2016-01-23 | 2020-02-11 | Michael Ray Stokes | Combined cycle energy recovery method and system |
| IT201700008681A1 (en) * | 2017-01-26 | 2018-07-26 | Nuovo Pignone Tecnologie Srl | GAS TURBINE SYSTEM |
| US20210080172A1 (en) * | 2017-05-10 | 2021-03-18 | Nuovo Pignone Tecnologie - S.R.L. | Compressor train arrangements |
| IT201900003077A1 (en) * | 2019-03-04 | 2020-09-04 | Nuovo Pignone Tecnologie Srl | CONFIGURATION OF MULTI-STAGE COMPRESSOR-EXPANDER TURBOMACHINE |
| JP2021025497A (en) * | 2019-08-07 | 2021-02-22 | 中国電力株式会社 | Intake gas cooling device, gas turbine plant, and intake gas cooling method |
| JP7362467B2 (en) * | 2019-12-20 | 2023-10-17 | 三菱重工コンプレッサ株式会社 | compressor system |
| WO2023241823A1 (en) * | 2022-06-16 | 2023-12-21 | Nuovo Pignone Tecnologie - S.R.L. | Dual purpose integrated gear for hybrid train application |
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| CN101498245A (en) * | 2008-01-31 | 2009-08-05 | 通用电气公司 | Power generating turbine systems |
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- 2013-08-01 RU RU2015101997A patent/RU2642714C2/en active
- 2013-08-01 KR KR1020157005043A patent/KR20150038412A/en not_active Application Discontinuation
- 2013-08-01 EP EP13745390.8A patent/EP2880266B1/en active Active
- 2013-08-01 US US14/419,278 patent/US20150176485A1/en not_active Abandoned
- 2013-08-01 JP JP2015524786A patent/JP2015524532A/en active Pending
- 2013-08-01 AU AU2013298557A patent/AU2013298557B2/en active Active
- 2013-08-01 CN CN201380041258.XA patent/CN104662258B/en active Active
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| CN101498245A (en) * | 2008-01-31 | 2009-08-05 | 通用电气公司 | Power generating turbine systems |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104662258A (en) | 2015-05-27 |
| US20150176485A1 (en) | 2015-06-25 |
| EP2880266B1 (en) | 2022-10-12 |
| BR112015001404B1 (en) | 2022-03-22 |
| RU2015101997A (en) | 2016-09-27 |
| RU2642714C2 (en) | 2018-01-25 |
| WO2014020104A1 (en) | 2014-02-06 |
| CA2880462C (en) | 2021-06-15 |
| BR112015001404A2 (en) | 2018-05-22 |
| ITFI20120161A1 (en) | 2014-02-04 |
| JP2015524532A (en) | 2015-08-24 |
| EP2880266A1 (en) | 2015-06-10 |
| AU2013298557A1 (en) | 2015-02-12 |
| AU2013298557B2 (en) | 2017-03-23 |
| KR20150038412A (en) | 2015-04-08 |
| CA2880462A1 (en) | 2014-02-06 |
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